Process for attacking a ground target from an airplane



United States Patent 11 1 3,538,809

[ 721' Inventor Ignaz Von Maydell [56] References Cited Munich. Germany UNITED STATES PATENTS [211 P 586,499 1,771,455 7 1930 Wiley .1 102/4 [22] Filed Oct. 13, 1966 P d N 10 1970 2,680,578 6/1954 Katz 102/3 [45] 3,149,531 9/1964 Musgrave s9/1.701 [73] Asslgnee Entwlcklungsrlng Sued Gmbl-I Munich, Germany OTHER REFERENCES 3 cm-pomfion G Popular Mechanics, October 1967, Over the Shoulder [32] P i i O t, 15, 1965 Bombing, by DelmerJ. Trester, pp 106-109. 298, 300-304 Germany Primary Examiner-Samuel WI Eugle E 30,284 AttorneyRobillard, Byrne, Baker, McKenzie and Hightower ABSTRACT: A method for attacking a ground target from an [54] PROCESS FOR ATTACKING AGROUND TARGET airplane including the steps of releasably securing a winged FROM AN AIRPLA NE I missile having adjustable control surfaces to an upper surface 14 Chums Drawmg of the airplane, flying the airplane at a low substantially con- [52] US. Cl .v 89/ 1.5, stant elevation and at a high speed past the target, setting the 244/3.l control surfaces on the missile for a flight pattern looping up- [51] Int. Cl F41f 5/02 wardly and rearwardly of the airplane and releasing the missile [50] Field of Search .0 89/ l, 1.5, from the airplane after passing the target while the airplane is 1.701, 244 at the same low Substantially constant elevation MOM 0001 7001 Patented Nov. 10, 1970 Sheet Sheet 3 of 6 Patented" Nov. 10, 1970- mated; Nav. 1o, 197o 3,538,809

INVENTOR. IGNA 2 van MA YDEL L arWMM/% LL ,Paiented Nov. 10,1910 3,538,@09

Sheet 5 of6 Fig-13 Fig. 15

- INVENTOR. lG/VAZ van MAYDELL BYZWMW A TTORNE'YS Patented Nov. 10, 1970 Sheet ATTORNEYS PROCESS FOR ATTACKING A'GROUND TARGET FROM AN AIRPLANE The invention herein relates to a weapons system, and more particularly to the method and means for attacking targets from a high speed low-flying plane during horizontal flight and with flying bodies such as glider bombs. Herein the flying bodies are released as the plane continues in its flight direction, greatly increasing the chances of survival of both the crew and plane and increasing the effectiveness of air-toground missions.

The progressing development of air defense techniques has greatly reduced, both the probability of survival and the effectiveness of the mission as it is presently flown. Even-the tactic of flying the missions at high speed low level flight have made little difference, because of decrease of airborne weapon effectiveness at high flight speeds and low altitudes. The overthe-shoulder weapon delivery technique, even at low level flight was also of little success, as the plane is exposed in an increased measure during the, time of weapon release to antiaircraft defense with the crews being subjected to extreme strain and the bombing accuracy being particularly poor.

Remote controlled rockets did not bring the progress hoped for as accuracy of fire increased only during slow flight (approximately 0.5 mach) and did not in the case of fast flying planes (about 1 mach). It is possible to achieve the increased accuracy of fire of remotely controlled rockets in slow flight but only at the expense of the payload, as the explosive head amounts to approximately one-third the load, and the rocket engines weigh twice as much as the explosive head, and sometimes more.

According to the invention herein, the conditions are fundamentally changed, as it is possible to increase by at least two and one-half to three times the weight of the explosive heads of the remotely controlled aircraft arm on a low level flight mission, as the heavy rocket engines are eliminated. The cost effectiveness of the entire weapons system, consisting of the aircraft, crew, supply-support, maintenance and aircraft arms thereby increase by two and one-half to three times.

Furthermore, it is possible to direct the airborne weapons during the initial run on the target as well as release them, thereby eliminating repetition of the run. Additionally, the target may be approached and crossed at the lowest'flight level, reducing exposure to antiaircraft fire to a minimum, thus insuring the safety of the crew and plane. The safety feature is also enhanced as the target may be approached and crossed at the highest possible speed, and this further decreased the effectiveness of antiaircraft.

Additionally, it is not necessary to cross directly over the target as it is possible to perform offset weapon release on targets spotted by the attacking plane in passing, even at highest speed and lowest flight altitude.

There is also eliminated the danger of being hit by bomb splinters despite flying at the lowest altitude, either above or laterally from the target. Hitherto self-inflicted damage to the aircraft could only be avoided at considerable expense, as by the use of droppable bodies with built-in air resistance whereby accuracy of fire was also considerably reduced. Additionally, it will now be possible to achieve a lateral spread of the bombs in low level flight from a single aircraft, and without repeating the run. As a matter of fact, it will be possible, even at the lowest flight level and at maximum speed, to drop a bomb carpet, not only on a target that is directly in line of flight but on targets the aircraft is passing although they are not in the line of flight.

The modes of attack are achieved because the drop devices need not be released until the aircraft has crossed over or by the target and is some distance therefrom, and this is done without the plane having to change flight direction, permitting the crew to concentrate entirely on the release and control of the drop devices onto the target. Because the release is subsequent to crossing or passing the target, the crew gains several precious seconds for spotting of the target and for making the decision as to release, a time period heretofore entirely lacking in the transonic low level flight.

The invention will be fully understood from the description herein, in view of the accompanying drawings, wherein:

FIG. 1 shows the course of an attack, viewed from the side, with a drop device whose-looping-shaped trajectory has been predetermined and fixed prior to its release;

FIG. 2 shows the course .of an attack, likewise viewed from the side, however with a drop device whose looping-shaped trajectory has been remote controlled in its last phase;

FIG. 3 shows the course of an'attack, viewed from the side, with several drop devices whose looping-shaped trajectories both in the direction of altitude as well as laterally have a different course;

FIG. 4 is a presentation of a course of attack corresponding to FIG. 3, however viewed from in front;

FIG. 5 shows thecourse of an attack, viewed from the side, with a drop device whose looping-shaped trajectory has been remote controlled in its last phase, whereby a fragmentation bomb containing several individual bombs is used as a drop device;

FIG. 6 shows the course of an attack according to FIG. 5, viewed from in front;

FIG. 7 shows the course of an attack, viewed from the side, with two decomposer bombs as drop devices, whose loopingshaped trajectories are remote controlled as early as their middle phase;

FIG. 8 shows the course of an attack corresponding to FIG. 7, viewed from in front;

FIG. 9 shows the course of three possibilities of an attack, viewed from the side, with in each case different loopingshaped trajectories of the drop devices, which can be predetermined;

FIG. 10 shows the course of an attack, viewed from the side, whereby a flare composition that is to be released at the zenith of the looping-shaped trajectory for the purpose of illuminating the area of combat is used as a drop device;

FIG. 11 shows, in perspective, an aircraft which is to be used in the case of the process in accordance with the invention, with drop devices arranged above the wings;

FIG. 12 shows in perspective an example of a control arrangement as required to carry out the process in accordance with the invention;

FIG. 13 shows diagrammatically an example of a selective switch for regulating the altitude of the trajectory and the distances of the trajectory;

FIG. 14 shows diagrammatically a safety arrangement as required to carry out the process in accordance with the invention, at top speed within the area of the thermodynamic barrier;

FIG. 15 shows the course of an attack in which the drop device in the phase a, has been under remote control by means of an orientation acid; and

FIG. 16 shows a space diagram corresponding to the process shown in FIG. 15. .j

Referring to FIGS. 1 and 11, the method of attack is to cross or pass the target 7 in horizontal, top speed, low level flight, at a point in time t continue for a distance a,, in the time period t to t, and at t,, launch the flying devices 10, which are releasably carried by the plane 1. The devices 10 have movable control surfaces, such as horizontal and vertical rudders or other comparable control means designated l2, l3 and 14 on the glider bombs 10 (FIG. 11) and 12', I3 and 14 on fragmentation bomb 10 (here used to include a splintering missile, or of releasing other bombs upon fragmentation). The control surfaces may be preset or may be adjusted by remote control from within the aircraft. The controls are set, so that the devices 10 upon their release at the point in time 1,, will fly be means of their kinetic energy and their wings 16, 16 in a loop-shaped aerodynamic trajectory opposite to the flight direction of the aircraft, or through any given flight path whose apex is at an altitude H sufficiently higher than the flight path of the aircraft, so that after a predetermined period of time as measured from t, to t; over a distance a.,, the bombs will impact on the target 7, and thus the time flight of the bomb and time flight of the plane are substantially the same.

Because of the elapsed time, when the device 10 impacts on the target 7 damage to the aircarft 1, flying at low level altitude H from the ground, will not occur as it has traveled the distance from the point of bomb release, and a, plus a from the overflight of the target and in the time period t to FIG. 2 illustrates how the loop-shaped trajectory of the drop devices 10 may be additionally influenced in the last phase through remote control devices. If several drop devices are carried by one aircraft, the horizontal control surfaces of the projectiles are set to describe several different loop-shaped trajectories as seen in FIG. 3, the time period t,- being sufficient to assure that the distance a, assures the plane being beyond the splinter area. As shown in FIG. 4, the loop-shaped trajectories of the drop devices may be deflected transversely, from the flight direction of the carrier aircraft, by different settings of the vertical rudders. If several drop devices are to be launched, the release would be simultaneously made through a single release arrangement.

The foregoing illustrates that it is possible to launch bomb carpets on targets previously passed in flight, and to cover wide areas transversely of the line of flight, although previously passed by the aircraft.

As stated earlier, the various patterns are obtained by setting the tail units 12, 13, 14 or 12, 13', 14' ofthe individual drop devices It), 10' (FIG. 11) as required, rasters being provided within a limited area of adjustment on the movable surfaces, that is, the elevators and/or rudders or ailerons, which permit a lockable adjustment of the movable surfaces in a predetermined pre-set raster position.

The drop devices (FIG. 11) are releasable carried on the upper surfaces of the wing and fuselage and, because of this, the direction of flight of the airplane does not have to be changed during the preliminary setting of the tail units of the drop devices during the phase of movement a or 'after the release of the drop devices and during the phase of movement The method of launching a fragmentation bomb l0 and remotely controlling its trajectory is illustrated by FIGS. to 8. FIG. 5 shows the trajectory of the bomb by remote control in the last phase of its flight, and in FIGS. 7 and 8, two such bombs are shown under separate remote controls in different trajectories prior to reaching their greatest altitude. In this case, as can be seen from FIG. 8, the bombs may be deflected laterally, and transversely to the line of flight of the aircraft.

Furthermore, it is possible to shape the loop-shaped trajectories differently, a special selector switch to serve this purpose will be subsequently described, the loop-shaped trajectories may be predetermined as can be seen from FIG. 9 to achieve various altitudes H, H, H". Also, various flying ranges a or a and a,, that is, from the time of flying over the target until the impact of the drop device on the target 7, so that the aircraft, at the time of impact of each bomb, has passed well beyond the danger zone.

The drop devices, which may be characterized as nonselfpropelled flying missiles, may be carried on the wings 2, above the wings, or preferably atop the fuselage of the aircraft, as shown in FIG. 11. In this instance, the construction of the tail unit as such that the missiles will not encounter any interference upon release. As shown, a double lateral tail unit 3 is provided on the aircraft, and the lateral distance 5 between the tail units and the vertical plane of symmetry of the plane is preferably more than one-half the entire span 15 between extreme wing tips of the wings 16 of the transversely positioned missiles.

For remote control, the missiles and plane are equipped with TV cameras which transmit to receiving station on the carrier aircraft 1. If dimly light-sensitive TV (low light level TV) cameras are provided in the missiles, it is possible to cut them in prior to the release, as aids to vision for the crew of the aircraft. In the case of drop devices, which will be under remote control, either prior to or after passing through the apex S of the trajectory, the remote control may be accomplished by any well known automatic guidance system, whereby the crew of the aircraft emits radio signals via a remote control sender, which signals are received within the flying device and cause an adjustment of the rudders. For night, twilight or early dawn missions, the remote control of the missiles may be accomplished with the "tangential method" of DBP-German Federal Pat. No. 1,182,965.

By using television cameras in the drop or flying devices, the trajectory of descent is remotely controlled by a member of the aircraft crew with the assistance of the TV picture transmitted to the aircraft receiver. The first orientation by the crew member directing the flying device, is accomplished in accordance with the TV picture. The view of the target photographed by the TV camera on the missile is, of course, different than that seen from the camera aircraft or visibly when possible. From the aircraft, the target is visible from the side, but from a flying device, during the descending trajectory, a birds eye view is obtained.

To facilitate the orientation during the first seconds of the remote control process, it is possible, if available, to use outstanding points of topography, such as a river, super highway, or seacoast. The target will always be in a certain geometric relationship to the total target scene. If such points are not available, points must be artificially created. This is accomplished because, after crossing over or passing the target, the flight path of the aircraft is made visible for a few seconds by generating artificial fog in the air be means of a spray device on the aircraft.

In the TV picture from the missile, the birds eye view will pick up the path, making the line of flight visible in the form of a white line of artificial fog on the terrain. In the summer, a white spray is used; in winter, black or some other dark color is used. The line in the terrain is always in a well defined geometric relationship to the target. At the target end, the line is wider, and at its remote end, narrower, corresponding to the time available for spreading of the dye.

The above is shown by FIG. 16 which depicts the remote control process by a space diagram in the case of an attack as viewed from the side of FIG. 15. In this case, the target 7 is a distance b from the flight path. As no outstanding topography points are available in relation to the target 7, the mountain ridges are not suitable for this purpose, the artificial strip of fog, designated by 65, is used for the orientation of the control gunner. 1

For practical purposes, with a two seater carrier aircraft, a rudder operating arrangement is provided for carrying out the method by switching to the TVs for the missiles carried abroad the aircraft, and simultaneously releasing the dual stick control. As seen from FIG. 12, mechanical reversing arrangements 25, 35, 45 are provided on each control shaft 20, 30, 40 which are, in effect, couplings with multipole changeover switches, which permit their use with an electric aircraft control.

If a single seater aircraft, with fully automatic control is used as the carrier aircraft, then the switching arrangements can be developed in such manner that after, or simultaneous with, the switching in of the autopilot for maintaining the course and the altitude and/or maintaining the altitude with regard to the ground, the stick and the pedals of the pilot may be switched over to operating elements of the remote control devices of the drop devices carried abroad the aircraft. The change-over means 25, 35, 45 will then be arranged between the autopilot and the stick or the pedals.

FIG. 12 shows an arrangement with the switch-over arrangements in perspective. The movement for the altitude and low level control have been designated by 21, 22, those for the lateral and course control with 31, 32 and those for transverse control with 41, 42. The switch-over arrangements 25, 35 45 on the control shafts 20, 30, 40 for elevator and low level control and those for the directional and aileron control, permit the switching in of the remote control devices for the drop devices, by the channels 28, 38, 48. The rod system, of the coupling change-over switch 61 to the individual coupling ar rangement, has been designated by 26, 36, and 46. The autopilot 60 is connected with the servo motors 29, 39, and 49 via the lines 27, 37 and 47.

The selector switch S0,shown by way of example in FIG. 13, includes control buttons 51, 52 to adjust the apex altitude H of the trajectory of thedrop device in relation to the speed of flight depending on the requirements, whereby the time period between the release and the impact of the drop devices on the target may be varied. By means of control knobs 53, 54, it is possible to adjust the time period between the overflight t of the target or the flight past a target, and the release of the drop device at The letter b" -in selector switch 50 designates the lateral distances of the target from the flight path, as seen in FIG. 16.

In order that lightening of the carrier aircraft will not result at the time of the release of the drop devices, the size of the wings 16, 16' of the drop devices and the adjustment of the elevators 12, 12' of the drop devices l0, 11 are dimensioned so that the lift components of the drop devices correspond at least to the weight of the drop devices. This will assure that, at the time of the release of the drop devices, deviations of the carrier aircraft from the flight path will not occur, particularly in relation to the flight altitude H, so that the carrier aircraft may remain at an altitude where it is least exposed to possible antiaircraft fire. Additionally, it is possible to decrease the probability of being exposed to antiaircraft fire at the time of approach to the target, by increasing speed to the permissible maximum, this being limited by the heating up of the aircraft. Safety devices reacting to increases in temperature of the aircraft are used to automatically throttle back the propulsion unit, soon after the launch of the drop devices,

when flying within the range of the thermodynamic barrier is not required. Such a safety arrangement 70 is shown diagrammatically by FIG. 14, in which the temperature sensing instruments 71 have been arranged at many points on the outer skin of the airplane, the sensing devices being connected by lines 72 to a regulating device 73, which upon an increase in temperature of the aircraft that could endanger its safety, automatically reduces the fuel supply by adjustment of the lever 74, thus reducing the speed of flight.

The method and means having been described, it should be recognized that the term passing the target means a fly-by whether directly over or to one side thereof. For simplicity and clarity, means have been identified, such as guidance system, TV cameras, or the like, without detailed and burdensome description, as it is well within the skill of the art to install standardized systems, when as herein the proper locations, purposes and results to be achieved are disclosed.

lclaim: I

l. The method of attacking a ground target from an airplane which comprises releasably securing at least one winged missile having adjustable control surfaces to an upper surface of the airplane; flying the airplane at a low substantially constant elevation and at a high speed past the target; setting the control surfaces on the missile for a flight pattern looping upwardly and in a direction opposite the line of flight of the plane and requiring a predetermined time before impact on the target; and releasing the missile from the plane after passing the target while the airplane is at the same low substantially constant elevation; the predetermined flight time for the missile being sumcient to enable the plane to fly beyond the bomb splinter area resulting from impact.

2. The method defined in claim 1 wherein the plane continues in low level high speed flight following release of the missile and for the time period between release of the missile and its impact on the target.

3. The method defined in claim 1 wherein the plane flies at a speed maximum automatically controlled by temperature sensing devices.

4. The method defined in claim 1 wherein the missile control surfaces are remotelyset from the plane after passing the target.

5. The method defined in claim 1 wherein the trajectory of the missile is remotel controlled from the aircraft.

6. The method de med in claim 1 wherein the trajectory of the missiles is in the same line of flight but opposite to that of the plane.

7. The method defined in claim 1 wherein the trajectory of the missile is oblique and opposite to the line of flight of the plane.

8. The method defined in claim 1 including spraying a color into the air upon reaching the target and continuing spraying in the line of flight of the plane; providing a line of reference.

9. The method defined in claim 1 including taking a picture of the target from the missile on its downward trajectory and transmitting the picture to the plane.

10. The method defined in claim 1 including securing more than one missile to the plane, setting the control surfaces of each missile for a flight pattern looping upwardly and opposite the line of flight of the plane, and with the angle of flight set differently for each missile.

11. The method defined in claim 10 including releasing the missiles simultaneously.

12. The method defined in claim 10 including releasing the missiles at pre-set time intervals in a predetermined sequence.

13. The method defined in claim 1 including providing the missile with a parachute and opening the parachute at the apex of the trajectory.

14. The method defined in claim 1 including releasably securing said missile to the fuselage above the wings of said airplane. 

